U.S. patent number 8,919,668 [Application Number 13/741,868] was granted by the patent office on 2014-12-30 for thrust reverser having a lockable variable nozzle section.
This patent grant is currently assigned to Aircelle. The grantee listed for this patent is Aircelle. Invention is credited to Philippe Avenel, Jean-Philipe Joret, Loic Le Boulicuat, Guy Bernard Vauchel.
United States Patent |
8,919,668 |
Vauchel , et al. |
December 30, 2014 |
Thrust reverser having a lockable variable nozzle section
Abstract
The present disclosure relates to a thrust reverser including at
least one translatably movable cowl capable of alternately shifting
between a closed position in which same ensures the aerodynamic
continuity of the nacelle and which covers the deflecting means,
and an open position in which same opens a passage in the nacelle
and uncovers the deflecting means, said thrust reverser likewise
including at least one variable nozzle section arranged in the
extension of the movable thrust-reversing cowl and provided with at
least one locking means capable of engaging with a complementary
locking means of the movable reversing cowl so as to optionally
mechanically link the movable nozzle section of the movable
reversing cowl.
Inventors: |
Vauchel; Guy Bernard (Harfleur,
FR), Joret; Jean-Philipe (Beuzeville, FR),
Le Boulicuat; Loic (Le Havre, FR), Avenel;
Philippe (Sainte Adresse, FR) |
Applicant: |
Name |
City |
State |
Country |
Type |
Aircelle |
Gonfreville l'Orcher |
N/A |
FR |
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Assignee: |
Aircelle (Gonfreville l'Orcher,
FR)
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Family
ID: |
43499964 |
Appl.
No.: |
13/741,868 |
Filed: |
January 15, 2013 |
Prior Publication Data
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Document
Identifier |
Publication Date |
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US 20130292489 A1 |
Nov 7, 2013 |
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Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
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PCT/FR2011/051151 |
May 20, 2011 |
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Foreign Application Priority Data
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Jun 3, 2010 [FR] |
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10 54324 |
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Current U.S.
Class: |
239/265.19;
60/230; 60/226.2; 239/265.33; 239/265.11 |
Current CPC
Class: |
F02K
1/62 (20130101); F02K 1/766 (20130101); F02K
1/09 (20130101); F02K 1/763 (20130101); F02K
1/72 (20130101); Y02T 50/671 (20130101); Y02T
50/60 (20130101) |
Current International
Class: |
B63H
11/00 (20060101); F02K 1/00 (20060101); F02K
3/02 (20060101); B63H 11/10 (20060101); B64D
33/04 (20060101) |
Field of
Search: |
;239/265.11,265.19,265.23,265.33 ;60/226.2,230 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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1457660 |
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Sep 2004 |
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EP |
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2358555 |
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Feb 1978 |
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FR |
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2622929 |
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May 1989 |
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FR |
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Other References
I PCT/FR2011/051151 International Search Report. cited by
applicant.
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Primary Examiner: Wongwian; Phutthiwat
Assistant Examiner: Goyal; Arun
Attorney, Agent or Firm: Brinks Gilson & Lione
Parent Case Text
CROSS-REFERENCE TO RELATED APPLICATIONS
This application is a continuation of International Application No.
PCT/FR2011/051151 filed on May 20, 2011, which claims the benefit
of FR 10/54324, filed on Jun. 3, 2010. The disclosures of the above
applications are incorporated herein by reference.
Claims
What is claimed is:
1. A thrust reverser for a turbine engine nacelle comprising: a
cascade grid mounted to the nacelle and configured to deflect at
least one portion of an airflow of the turbine engine, and; at
least one translationally movable cowl along a substantially
longitudinal direction of the nacelle, the at least one
translationally movable cowl capable of alternately passing from a
closing position to an opening position, wherein in the closing
position, said at least one translationally movable cowl provides
an aerodynamic continuity of the nacelle and covers the cascade
grid, and in the opening position, said at least one
translationally movable cowl opens a passage in the nacelle and
uncovers said cascade grid; and an internal panel configured to
translate along said longitudinal direction and causes blocking
flaps to pivot, wherein said at least one translationally movable
cowl comprises at least one variable nozzle section arranged in an
extension of said at least one translationally movable cowl and
wherein said at least one translationally movable cowl is equipped
with at least one locking means capable of cooperating with an
additional locking means of said internal panel so as to
mechanically link said internal panel to said at least one
translationally movable cowl; wherein the locking means and the
additional locking means comprise at least one movably mounted
ratchet compressed against an elastic return means, the at least
one movably mounted ratchet capable of moving between an engagement
position and a disengagement position, wherein in the engagement
position, the at least one movably mounted ratchet firmly attaches
said internal panel to said at least one translationally movable
cowl to pivot said blocking flaps and in the disengagement
position, the at least one movably mounted ratchet releases the
internal panel from said at least one translationally movable cowl
for a variable nozzle mode, the elastic return means tending to
bring the at least one movably mounted ratchet back into said
engagement position, said at least one movably mounted ratchet
being maintained in the disengagement position via at least one pin
mounted on a fixed structure of the thrust reverser, wherein in
said variable nozzle mode, said at least one translationally
movable cowl translates while said internal panel remains
fixed.
2. The thrust reverser according to claim 1, wherein the at least
one pin is movably mounted between a position for maintaining the
at least one movably mounted ratchet and a set-back position,
wherein the at least one pin passing from the position for
maintaining the at least one movably mounted ratchet to the
set-back position is combined with a situation of locking or
unlocking of the at least one translationally movable cowl on the
fixed structure.
3. The thrust reverser according to claim 1, characterized in that
it comprises a means for detecting the end of closure of the at
least one translationally movable cowl.
4. The thrust reverser according to claim 1, further comprising at
least one single rod actuator cylinder having a first end mounted
on the fixed structure and a second driving end linked to the
variable nozzle section.
5. The thrust reverser according to claim 1, wherein the fixed
structure on which the at least one pin is mounted, is a so-called
twelve o'clock beam.
6. The thrust reverser according to claim 1, wherein the at least
one translationally movable cowl is equipped with at least one
locking means with a front frame.
7. The thrust reverser according to claim 1, the at least one
locking means are located in a downstream portion of the at least
one translationally movable cowl.
8. The thrust reverser according to claim 1, wherein the at least
one locking means of the at least one translationally movable cowl
and/or of the at least one variable nozzle section is mounted on a
structure for guiding said at least one translationally movable
cowl and/or the variable nozzle section.
9. The thrust reverser according to claim 8, wherein the at least
one locking means comprises at least one jointed or sliding
abutment, the at least one locking means being located
substantially at a center of a section of a corresponding structure
for guiding said at least one translationally movable cowl or the
variable nozzle section.
10. A turbine engine nacelle comprising at least one thrust
reverser according to claim 1.
Description
FIELD
The present disclosure relates to a nacelle for an aircraft engine,
equipped with a thrust reversal device extended with a nozzle
device with variable section.
BACKGROUND
The statements in this section merely provide background
information related to the present disclosure and may not
constitute prior art.
An airplane is driven by several turbine engines each accommodated
in a nacelle used for channeling the airflows generated by the
turbine engine which also harbors a set of ancillary actuation
devices related to its operations and ensuring diverse functions
when the turbine engine is operating or at a standstill.
These ancillary actuation devices notably comprise a mechanical
system for thrust reversal and a variable nozzle system.
A nacelle generally has a tubular structure comprising an air
intake upstream from the turbine engine, a middle section intended
to surround a fan of the turbine engine, a downstream section
harboring thrust reversal means and intended to surround the
combustion chamber of the turbine engine, and it is generally
completed with an ejection nozzle, the outlet of which is located
downstream from the turbine engine.
Modern nacelles are intended to harbor a dual flow turbine engine
capable of generating via the rotating blades of the fan a flow of
hot air (also called primary flow) from the combustion chamber of
the turbine engine, and a cold air flow (secondary flow) which
circulates outside the turbine engine through an annular passage,
also called a vein, formed between a fairing of the turbine engine
and an internal wall of the nacelle. Both air flows are ejected
from the turbine engine through the rear of the nacelle.
The role of a thrust reverser during the landing of an airplane is
to improve the braking capability of the latter by redirecting
forwards at least one portion of the thrust generated by the
turbine engine. In this phase, the reverser shuts off the vein of
the cold flow and directs the latter towards the front of the
nacelle, thereby generating a counter thrust which will be added to
the braking of the wheels of the airplane.
The means applied for achieving this reorientation of the cold flow
vary according to the reverser type. However, in all cases, the
structure of a reverser comprises movable cowls which may be
displaced between a deployed position in which they open in the
nacelle a passage intended for the deflected flow on the one hand,
and a retracted position in which they close this passage on the
other hand. These cowls may fulfill a deflection function or a
function simply for activating other deflection means.
In the case of a reverser with grids, also known as a cascade
reverser, the reorientation of the air flow is carried out by
deflection grids, the cowl only having a simple sliding function
aiming at uncovering or covering these grids, the translation of
the movable cowl being carried out along a longitudinal axis
substantially parallel to the axis of the nacelle. Additional
blocking gates, activated by the sliding of the cowling, generally
allows the vein to be closed downstream from the grids so as to
optimize the reorientation of the cold flow.
In addition to its thrust reversal function, the sliding cowl
belongs to the rear section and has a downstream side forming an
ejection nozzle aiming at channeling the ejection of the air flows.
This nozzle may be an addition to a primary nozzle channeling the
hot flow and is then called a secondary nozzle.
The performances of thrust reversal are satisfactorily obtained
with the known devices. However, for reasons of aerodynamic
optimization, and consequently optimization of fuel consumption, it
is quite advantageous to be able to adjust the section of the
outlet for the cold air flow downstream from the nacelle: it is
indeed useful to be able to increase this section during take-off
and landing phases, and to reduce it during cruising phases: this
is often referred to as an adaptive nozzle, or else further as a
"VFN" (Variable Fan Nozzle).
Such a system is described in document FR 2 622 929 or further FR 2
902 839 for example.
These documents describe the application of thrust reversers with
grids, equipped with a variable ejection section and to do this
provides a movable cowl comprising two portions which may be
connected together with locking means.
According to the embodiments, the variable nozzle may be made from
one or several dedicated movable elements, such as pivoting flaps
or a translatable cowl portion or this function may be fulfilled by
the movable cowl itself by low amplitude translational movements
not activating the thrust reversal function.
For an extensive and detailed description of different embodiments,
reference may be made to documents FR 2 922 058, FR 2 902 839, FR 2
922 059, inter alia.
The operating phases of the variable nozzle and of the thrust
reverser are distinct. The variable nozzle can only operate when
the reverser is actuated upon landing. Vice versa, the thrust
reverser should not operate when the variable nozzle section is
maneuvering.
Moreover, the adaptive nozzle is located in the downstream
extension of the thrust reversal cowl, and it is important to be
able to actuate both of these portions of the nacelle
independently; in particular the intention is to be able to
increase the section of the adaptive nozzle without actuating the
thrust reversal means, in particular during take-off.
In order to achieve this independent actuation, each movable
portion (reverser/nozzle) may conventionally be equipped with its
own actuator (two single rod actuators or a dual rod actuator
cylinder, for example) and be driven independently.
In order to make the driving assembly lighter, it is possible to
use a simple single-rod actuator, by providing additional locking
means between the movable portions.
Such a solution and a few application principles are shown in
document FR 2 902 839, notably in FIGS. 13 to 15.
SUMMARY
The present disclosure is directed to a locking system between a
movable reverser portion and a movable nozzle portion for actuation
by means of at least one single-rod cylinder.
It should be noted that although more particularly intended for an
actuation system with a single-rod cylinder, the invention is not
limited to this type of driving means and is independent of this,
the locking of both movable structures together may be used with
other types of driving means and may further form an additional
defense line in certain cases.
The present disclosure relates to a thrust reverser for a turbine
engine nacelle comprising means for deflecting at least one portion
of an air flow of the turbine engine on the one hand, and at least
one translationally movable cowl along a substantially longitudinal
direction of the nacelle capable of alternately passing from a
closed position in which it ensures aerodynamic continuity of the
nacelle and covers the deflection means, and an opening position in
which it opens a passage in the nacelle and uncovers the deflection
means on the other hand, said thrust reverser also comprising at
least one variable nozzle section arranged in the extension of the
thrust movable reversing cowl and equipped with at least one
locking means capable of cooperating with an additional locking
means of the movable reversing cowl so as to mechanically link the
movable nozzle section to the movable reversing cowl or not,
characterized in that the locking means and the additional locking
means comprise at least one locking ratchet movably mounted against
an elastic return means between an engagement position in which it
firmly attaches the drive of the nozzle section and of the reversal
cowl, and a disengagement position in which it releases the drive
of said nozzle section and of said reversal cowl, the elastic
return means tending to bring the ratchet back into its engagement
position, said ratchet being maintained in a disengagement position
via at least one pin mounted on the fixed structure of the
reverser.
Thus, by providing a locking system activated by a pin, a simple,
reliable and efficient mechanical locking system is made available,
not requiring complex linkages, and with which it is possible to
meet the requirements mentioned above.
It should be noted that according to certain embodiments, the
reversal function and the movable nozzle function may be fulfilled
by a same external movable cowl, with low amplitude displacements
ensuring the nozzle section variation, while a large amplitude
displacement will activate the reversal function. This is notably
the case in document FR 2 902 839.
In such a form, the locking is then carried out with a movable
interior portion only open during the operation in the reverser
mode. The term of movable reversing cowl should then be understood
with broad acceptance designating a moveable portion only activated
in the reverser mode.
Advantageously, the pin is movably mounted between a position for
maintaining the movable ratchet and a set back position, the
passing from one position to the other being associated with a
locking or unlocking situation of the movable reversing cowl on the
fixed structure.
Advantageously, the device comprises a means for detecting the end
of the closing of the movable reversing cowl.
In one form, the thrust reverser comprises at least one single rod
cylinder having a first end mounted on the fixed structure and a
second driving end, linked to the movable nozzle section.
In another form, the fixed structure on which the pin is mounted,
is a longitudinal beam, and more particularly a so called twelve
o'clock beam.
In another form, the movable reversing cowl is equipped with at
least one locking means with a fixed structure of the reverser,
notably a front frame.
Still in another form, the locking means are located in an upstream
portion of the movable reversing cowl.
Advantageously, the locking means of the movable reversing cowl
and/or of the movable nozzle are mounted on a guiding structure of
said movable reversing cowl and/or nozzle.
In one form, the locking means comprises at least one jointed or
sliding abutment, preferably located substantially in the center of
a section of the corresponding guiding structure if necessary.
Advantageously, the locking system is located in an upper portion
but may also be located in a lower portion.
Still advantageously, at least one guiding rail of the variable
nozzle is in abutment downstream in a guiding rail of the reversal
cowl, with a functional maneuvering play of the abutment on the
blocking nozzle structure being provided.
The present disclosure also relates to a turbine engine nacelle
characterized in that it comprises at least one thrust reverser
according to the invention.
Further areas of applicability will become apparent from the
description provided herein. It should be understood that the
description and specific examples are intended for purposes of
illustration only and are not intended to limit the scope of the
present disclosure.
DRAWINGS
In order that the disclosure may be well understood, there will now
be described various forms thereof, given by way of example,
reference being made to the accompanying drawings, in which:
FIG. 1 is a general longitudinal sectional view of a thrust
reversal device according to the disclosure;
FIGS. 2 to 8 schematically illustrate the different operating steps
of the thrust reverser of FIG. 1;
FIGS. 9 and 10 schematically illustrate an alternative embodiment
of the thrust reverser of FIG. 1, the locking system being equipped
with a movable pin; and
FIGS. 11 and 12 schematically illustrate a second alternative form
of the thrust reverser of FIG. 1, the locking system being equipped
with a movable pin associated with an end-of-travel detector.
The drawings described herein are for illustration purposes only
and are not intended to limit the scope of the present disclosure
in any way.
DETAILED DESCRIPTION
The following description is merely exemplary in nature and is not
intended to limit the present disclosure, application, or uses. It
should be understood that throughout the drawings, corresponding
reference numerals indicate like or corresponding parts and
features.
FIG. 1 is a general longitudinal sectional view of a thrust
reversal device 1 according to the invention, as notably described
in document FR 2 902 839.
The thrust reversal device 1 belongs to the rear section of a
nacelle (not shown) of a turbine engine, is mounted on a front
frame 100. The rear section defines with an internal bearing
structure of the turbine engine, a vein 2 for circulation of a
secondary air flow.
The thrust reversal device comprises a translationally movable cowl
3 along a substantially longitudinal direction of the nacelle
capable of being translationally driven by a single rod actuator
cylinder 101 so as to alternately pass from a closing position
(FIG. 1) in which it harbors deflection grids (not visible) and
ensures structural and aerodynamic continuity of the nacelle, the
secondary flow then being ejected directly through the vein 2, to
an opening position in which it uncovers said deflection grids,
then opening a passage in the nacelle, an internal panel 4 also
mounted so as to be translationally movable, causing the pivoting
of blocking flaps 5 which will shut off totally or partly the vein
2 so as to force ejection of a secondary flow through the
deflection grids substantially towards the front of the nacelle in
order to generate a counter thrust.
The single rod cylinder 101 has a base 101a mounted on the front
frame, fixed, and a movable end 101b, linked to the cowl 3 to be
moved.
Moreover, the movable cowl 3 has a downstream end 3a able to be
used as a variable nozzle section.
To do this, in addition to the large amplitude translations
(maximum deployed cylinder 101) allowing clearing of the deflection
grids and activation of the thrust reversal function, said movable
cowl 3 performs low amplitude displacements, not causing clearing
of the deflection grids or opening of the nacelle.
Thus, it is understood that in the case of operating in thrust
reverser mode, the movable cowl 3 and the internal panel 4 have to
perform translation upstream from the nacelle in a large amplitude
movement while in the case of operating in a variable nozzle mode,
only the movable cowl 3 moves according to reduced amplitude
movements, the internal panel remaining fixed so as to ensure the
internal fairing of the vein 2.
As discussed in document FR 2 902 839, removable locking means
should then be provided between the movable cowl 3 and the internal
panel 4.
Thus, in a thrust reversal mode, the movable cowl 3 and the
internal panel 4 are locked together, the internal panel 4 then
simultaneously performing a translational movement to the movable
cowl 3, while in the variable nozzle mode, the movable cowl 3 and
the internal panel 4 are unlocked, the movable cowl 3 can then no
longer drive the internal panel 4 which remains motionless.
Moreover, the internal panel is itself locked on the front frame
100 when the thrust reversal function is deactivated. In this case,
the locking is performed by means of a hook 105 capable of engaging
with a corresponding locking finger 106.
The present disclosure thus provides a simple and reliable locking
system as discussed earlier.
To do this, the thrust reversal device 1 is equipped with a locking
system 200, the structure and the operation of which will now be
described in detail.
The locking system 200 comprises a first locking means 201
belonging to the movable cowl 3 and capable of cooperating with an
additional locking means 202 of the internal panel 4 so as to
mechanically link the movable cowl 3 and the internal panel 4 or
not, as explained above.
In this case, the locking means 201 appears as a dog and the
additional locking means 202 appears as a ratchet capable of
engaging with the dog when it is facing the latter. Quite
obviously, the dog and the ratchet may be positioned vice versa on
the internal panel 4 and the movable cowl 3, respectively.
The ratchet 202 is movably mounted against an elastic return means
appearing as a spring 203 tending to force it towards its
engagement position.
Finally, the locking system comprises a pin 205 mounted on a fixed
structure of the reverser 1, notably for example, a twelve o'clock
longitudinal holding beam (not visible) and along which the movable
cowl 3 performs translation, said pin 205 being mounted so as to
maintain the ratchet 202 in its position for disengaging the dog
201 against the spring 203.
FIGS. 2 to 8 illustrate the operation of the locking system during
the diverse operating phases of the thrust reversal device.
FIG. 2 shows the locking system in the cruising position. In this
flight configuration, only the variable nozzle is operational. The
internal panel 4 is locked on the front frame 100 via the hook 105
engaged with the locking finger 106. The fixed pin 205 is located
at the locking ratchet 202 and maintains it in the disengagement
position against its spring 203. The dog 201, firmly attached to
the movable nozzle cowl 3, freely moves under the effect of the
actuation cylinder 101 in the variation range of the nozzle. The
nozzle section is here reduced to a minimum, the dog coming into
abutment against an upstream abutment.
FIG. 3 illustrates the opposite extreme position, i.e. the one in
which the nozzle section is maximum, the dog 201 coming into
abutment against a downstream abutment of the internal panel 4.
FIGS. 4 to 7 illustrate the passing into the thrust reversal
mode.
In this phase, the internal panel 4 is released from the front
frame 100 by opening the hook 105. By doing this, the dog 201,
still moving back under the effect of the cylinder 101, drives the
internal panel 4. The ratchet 202 then moves away from the fixed
pin 205 which no longer maintains it in an opening position against
its spring 203. The ratchet 202 then switches to the locking
position and will engage the dog 201, linking the internal panel 4
to the movable cowl 3, causing simultaneous displacement of both
structures.
Thus, the movable cowl 3 opens the external passage in the nacelle
and uncovers the deflection grids at the same time as the internal
panel 4 moves back and opens the internal passage in the vein 2 for
circulation of the secondary flow, which will also cause pivoting
of the blocking flaps 5.
When the thrust reversal phase is completed, and the movable cowl 3
and the internal panel 4 are retracted in the closing position of
the reverser, the ratchet 202, as illustrated in FIGS. 5 and 6,
returns towards the pin 205 which will force its opening and cause
disengagement of the ratchet 202 with the dog 201, thereby
releasing the internal panel 4 from the movable cowl 3.
The end of the reversal phase is completed, as illustrated in FIG.
7, by the relocking of the internal panel 4 on the front frame 100
with the hook 105.
FIG. 8 shows the return to the cruising configuration, identical
with FIG. 1.
FIGS. 9 and 10 show a first alternative embodiment of the locking
system in which the pin 205 is movably mounted on its fixed
structure, and more specifically is retractable by means of a
dedicated actuator 206.
This actuator 206 is driven in combination with the locking hook
105 on the front frame 100 by a control line 207.
Indeed, in the first form, it was seen that a short instant existed
between the moment when the movable cowl 3 is in abutment
downstream and initiates switching to the reversal phase, an
instant during which the movable cowl 3 is not locked with the
internal panel 4, the latter having to move beforehand slightly
away from the non retractable fixed pin 205 so that the ratchet 202
may tilt and engage with the dog 201.
By means of a retractable 206 control pin 205, in combination with
the hook 105, the pin 205 may be retracted, and consequently the
movable cowl 3 and the internal panel 4 may be locked together, as
soon as the hook 105 opens notifying the passing into the thrust
reversal mode.
A localization of the locking system 2001 as most downstream as
possible will advantageously be preferred in order to provide
sufficient distance with the locking of the internal panel 4 on the
front frame 100. Thus, in the case of bursting of a turbine vane,
the pin 205 will be used as a third defense line, notably by
providing an additional abutment belonging to the reversing
structure, in this case, the internal panel 4, which, positioned
upstream from the locking system, will prevent any unexpected
maneuver as long as said pin 205 is not retracted.
The locking system 2001 may comprise additional position sensors
giving the possibility of confirming the position of the different
movable portions so as to ensure execution of the different
maneuvers only when said movable portions are in the corresponding
configurations in order to avoid any risk of deterioration of the
parts.
In a third form schematically illustrated in FIGS. 11 and 12, the
locking system 2002 will comprise in addition to the retractable
206 pin 205, activation 209 by a closure end-of-travel detection
means 210 (FIG. 12). This gives the possibility of obtaining an
abutment for approaching a ramp of the ratchet 202 instead of using
the pin 205 as a pusher for forcing the ratchet 202.
Indeed, in the second form, the retractable 206 pin 205 is a
pushing pin. Further, it is driven by the locking system which has
to take into account the risk of jamming in its dimensioning. This
may lead to over dimensioning the system, which will have a
negative impact on the cost and the mass of the assembly.
In this third form, the retractable 206 pin 205 may be used as a
ramp and may be positioned in interference with the ratchet 202
before the latter comes into contact with it. It is then the
cylinder 101 for driving the movable cowl 3 which causes the
retractable pin 205 to retract. As the cylinder 101 is dimensioned
for larger loads, this additional force is transparent for said
cylinder 101. There is therefore no impact on the mass and the
cost.
Thus, in a position close to the complete closing of the thrust
reversal mode, the detection means 210 tells the locking system
2002 to deploy the pin 205. Said pin 205 is deployed before the
ratchet 202 comes into contact with it. At the same time, the hook
105 for locking the internal panel 4 on the front frame 100 is
engaged with the locking finger 106 so as to prevent any possible
unexpected backward movement of the structure. Thus, FIG. 12 shows
a transient position in which there no longer exists any movable
structure, (movable cowl 3 and internal panel 4) which is not
contained, complete disengagement of the ratchet 202 only being
carried out when the locking hook 105 is totally engaged.
Although the invention has been described with a particular
embodiment, it is by no means limited thereto and that it comprises
all the technical equivalents of the described means as well as
their combinations if the latter enter the scope of the
invention.
* * * * *